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2003-05-02: This amendment adopts a new airworthiness directive (AD) that applies to all aircraft (specifically balloons) that incorporate certain Lindstrand Balloons Ltd (Lindstrand) fuel hoses. This AD requires you to inspect for certain batches of installed fuel hoses and replace any of these fuel hoses. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect and replace defective fuel hoses before they result in propane fuel leaks. Such propane fuel leaks could lead to a propane fuel fire.
70-22-04: 70-22-04 WOOD ELECTRIC: Amdt. 39-1096 as amended by Amendment 39-1207. Applies to Aircraft Incorporating Wood Electric Corp Model 105, 106, 107, 108, 147, 152, 254, 447, 448, or 2100 series circuit breakers. Compliance required as indicated: (a) Within the next 500 hours' time in service after the effective date of this AD, unless already accomplished within the last 250 hours' time in service, and thereafter at intervals not to exceed 750 hours' time in service from the last check; to detect jammed circuit breakers, manually open and close all Wood Electric Corp. Model 105, 106, 107, 108, 147, 152, 254, 447, 448, and 2100 series circuit breakers installed in aircraft. All circuit breakers found jammed must be replaced prior to further flight. This check is not required when the modification in Paragraph (b) has been accomplished. (b) Within the next 1250 hours' time in service after the effective date of this AD, unless already accomplished, modify all Wood ElectricCorp. 105, 106, 107, 108, 147, 152, 254, 447, 448 and 2100 series circuit breakers by installing a ring manufactured in accordance with Wood Electric Corp. Drawing Number 64-008 Rev. No. 2 dated June 26, 1970 or later revision or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. To accomplish the modification, position the circuit breaker in either the closed or opened position and place the ring below the step (cap) portion of the button and above the threaded mounting neck of the circuit breaker. Exert enough finger pressure to snap the ring into place. Manually open and close the circuit breaker to insure proper positioning of the ring. (c) Upon request with substantiation data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (d) The check required by this AD may be performed by the pilot and the modification required by this AD constitutes preventive maintenance and may be performed by persons authorized to perform preventive maintenance under FAR 43. (Wood Electric Corp. Drawing Number 99-001 Rev. 1 dated June 26, 1970; Boeing Model 707/720 Service Bulletin 2693 Rev. 3 dated July 1, 1970; Boeing Model 727 Service Bulletin 24-35 Rev. 3 dated July 1, 1970 and Boeing Model 737 Service Bulletin 24-1019 Rev. 3 dated July 20, 1970 pertain to the modification required by this AD.) Amendment 39-1096 was effective November 4, 1970. This Amendment 39-1207 is effective May 19, 1971.
82-05-05 R1: 82-05-05 R1 FAIRCHILD SWEARINGEN: Amendment 39-4369. Applies to Models SA227-AC (S/N's AC-420 through AC-481, AC-485 through AC-491, AC-496 through AC-499 and AC-503), SA227-AT (S/N's AT-423 through AT-446, AT-454 through AT-487 and AT- 501), and SA227-TT (S/N's TT-421 through TT-462, TT-468 through TT-480 and TT-486 and TT-426A, TT-444A, TT-456A, TT-459A, TT-462A, TT-468A, TT-477A, TT-483A, TT-486A, and TT-489A) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To prevent propeller ice accumulation and potentially hazardous severe aircraft vibration, within the next five hours time-in-service after the effective date of this AD accomplish the following: a) Install black electrician's tape or equivalent over the words "AND ICING CONDITIONS" in the Approved Types of Operations Section of the Operating Limitations Placard which is located above the left side console. b) Install a temporary placard of 1/4-inch minimum lettering which states "NOT APPROVED FOR FLIGHT IN ICING" in front of and in clear view of the pilot and operate the airplane in accordance with this placard. c) In the Approved Types of Operation Section of the Operating Limitations placard shown in Section I, Limitations Section, of the Model SA227-AC Airplane Flight Manual (AFM) and in Section II, Limitation Section, of the Models SA227-AT and -TT AFM, delete or cover the words "AND ICING CONDITIONS." d) The placard and AFM changes required by this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person who must make the prescribed entry in the Airplane Maintenance Records indicating compliance with this AD. e) An equivalent method of compliance with this AD may be used when approved by the Chief, Aircraft Certification Division, FAA, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. The procedures contained in Fairchild Swearingen SA227 Series Alert Service Bulletin SB A 61-002 PROPELLERS-LEADING EDGE PROTECTION dated February 26, 1982, if accomplished in entirety are approved as an equivalent method of compliance with this AD. This amendment becomes effective on May 3, 1982, to all persons except those to whom it has already been made effective by a priority letter from the FAA dated February 26, 1982, and is identified as AD 82-05-05.
2003-05-01: This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of WSK PZL-Rzeszow S.A. Franklin 6A-350-C1, -C1A, -C1L, -C2, -C2A, and 4A- 235 series reciprocating engines. This action requires removing diaphragm type AC4886 fuel pump, AC part number (P/N) 5656774, PZL P/N 26.11.1710, before further flight, and prohibits installing diaphragm type AC4886 fuel pump, AC P/N 5656774, PZL P/N 26.11.1710. This amendment is prompted by several reports of failures of the valves and diaphragms in certain diaphragm type AC4886 fuel pumps, AC P/N 5656774, PZL P/N 26.11.1710, and adds the 6A-350-C1R engine to the applicability. The actions specified by this AD are intended to prevent reduction or loss of engine power or external fuel leaks.
2003-04-27: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier CL-600-2C10 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate functional and operational checks of the active and standby actuators of the rudder travel limiter (RTL) system. The actions specified by this AD are intended to prevent a significant latent failure in the RTL, which could lead to a critical loss of RTL function under certain conditions, and consequent loss of controllability of the airplane or structural damage. This action is intended to address the identified unsafe condition.
69-03-03: 69-03-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-719. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance required as indicated, unless already accomplished. To prevent possible jamming of aileron controls due to the aileron tab filler and modification plate assembly block, Part Number AB11/A1303 or AK11/A499, coming loose and fouling between the aileron and the wing structure, accomplish the following: (a) Within 75 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 150 hours' time in service from the last inspection, inspect the right and left aileron tabs for proper bonding within the tab structure of the filler and modification plate assembly P/N AB11/A1303 or AK11/A499 in accordance with British Aircraft Corporation BAC 1-11 Alert Service Bulletin No. 57-A-PM 3793, Issue 2, or later ARB-approved issue or FAA- approved equivalent. (b) If the filler and modification plate assembly is found to be loose during the inspection required by paragraph (a), before next flight, remove the assembly completely, and re- install the modification plate in accordance with BAC Modification No. 3793. (c) The repetitive inspections required by paragraph (a) of this AD may be discontinued after the existing filler and modification plate assembly is permanently secured by the addition of a 1/8" diameter blind rivet or after the incorporation of BAC Modification No. 3793. This amendment becomes effective February 14, 1969.
98-09-10: This amendment adopts a new airworthiness directive (AD) that applies to all EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300 and EA-300S airplanes. This AD requires inspecting the rudder control cables to assure that correctly swaged Nicopress type sleeves are installed at each end of the cables, and replacing any cable assembly where correctly swaged Nicopress type sleeves are not installed. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent a control cable from pulling through an incorrectly swaged sleeve, which could result in loss of rudder control with consequent loss of control of the airplane.
2011-27-51: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires inspecting the elevator bob-weight and attaching linkage for correct installation and for damage or deformation to the weight and/or weight bracket with corrective action as necessary. This AD was prompted by reports of the elevator bob-weight (stabilizer weight) traveling past its stop bolt, which allowed the attaching linkage to move over-center, resulting in reduced nose down elevator control, which could result in loss of control of the airplane. We are issuing this AD to detect and correct conditions that could result in reduced nose down elevator control and loss of control of the airplane.
2003-04-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 1900D airplanes. This AD requires you to inspect the alternating current (AC) inverter and modify the AC inverter and inverter sync wire shield. This AD is the result of reports that electrical noise causes the inverter to shut down in flight with loss of AC-powered flight instruments. The actions specified by this AD are intended to prevent electrical noise causing the inverter to shut down, which could result in failure of key aircraft electrical systems. Such failure could lead to loss of flight instruments during flight.
55-15-06: 55-15-06 LOCKHEED: Applies to 049, 149 Aircraft, Serial Numbers 1963 Through 1980, 2021 Through 2088; 649-749 Aircraft, Serial Numbers 2503 Through 2590, 2610, 2611, 2614 Through 2618; 1049C Aircraft, Serial Numbers 4501 Through 4548; 1049E Aircraft, Serial Numbers 4549 Through 4555, 4558, 4559, and 4563 Through 4565; 1049D Aircraft, Serial Numbers 4163 Through 4166. Compliance required by April 1, 1956, for Model 1049 aircraft and October 1, 1956, for Models 049/149 and 649/749 aircraft. To improve the fire-resistance integrity of the above aircraft, revisions to the system supplying cooling air to the accessory section of the powerplant installation are considered necessary. For 049-149 aircraft and 649-749 aircraft, the revision consists of installing a shutoff valve in a fireproof duct. For the 1049C and E aircraft, the revision consists of replacing a section of aluminum duct between the oil cooler scoop, and the existing shutoff valve, with a fireproof duct. This section is in zone 1, and provides a possible zone 1 to zone 2 firepath. Lockheed Service Bulletins 49/718, for 049/149 aircraft; 1049/2384, for 1049 aircraft; and 49/391A, for 649-749 aircraft, cover these subjects.